Aircraft and airborne electrical power and thermal management system

ABSTRACT

A unique airborne electrical power and thermal management system and a unique aircraft having a unique airborne electrical power and thermal management system are provided. The electrical power and thermal management system includes a turbine, which may power loads, for example but not limited to, a generator and a refrigerant compressor. The turbine may be in fluid communication with a gas turbine engine bleed air source to extract power from bleed air for powering the loads. A combustor may be fluidly disposed between the bleed air source and the turbine. The turbine may be part of a gas turbine engine distinct from a propulsion gas turbine engine. In one aspect, at least a portion of the electrical power and thermal management system may be disposed within an aircraft external pod. The pod may be configured to appear similar to a conventional external fuel tank pod employed by the aircraft.

CROSS REFERENCE

The present application claims the benefit of U.S. Provisional PatentApplication No. 61/468,387, filed Mar. 28, 2011, which is incorporatedherein by reference.

FIELD OF THE INVENTION

The present invention relates to aircraft, and more particularly, to anaircraft having an airborne electrical power and thermal managementsystem.

BACKGROUND

Airborne systems that effectively provide electrical power and managethermal energy remain an area of interest. Some existing systems havevarious shortcomings, drawbacks, and disadvantages relative to certainapplications. Accordingly, there remains a need for furthercontributions in this area of technology.

SUMMARY

One embodiment of the present invention is a unique airborne electricalpower and thermal management system. Another embodiment is a uniqueaircraft. Other embodiments include apparatuses, systems, devices,hardware, methods, and combinations for aircraft and electrical powerand thermal management systems. Further embodiments, forms, features,aspects, benefits, and advantages of the present application will becomeapparent from the description and figures provided herewith.

BRIEF DESCRIPTION OF THE DRAWINGS

The description herein makes reference to the accompanying drawingswherein like reference numerals refer to like parts throughout theseveral views, and wherein:

FIG. 1 illustrates an aircraft employed in accordance with an embodimentof the present invention.

FIG. 2 schematically illustrates an electrical power and thermalmanagement system operating to provide electrical power to and managethermal energy for a system in accordance with an embodiment of thepresent invention.

FIG. 3 schematically illustrates a non-limiting example of some aspectsof an electrical power and thermal management system in accordance withan embodiment of the present invention.

FIG. 4 schematically illustrates a non-limiting example of some aspectsof an electrical power and thermal management system in accordance withan embodiment of the present invention.

FIG. 5 schematically illustrates a non-limiting example of some aspectsof an electrical power and thermal management system in accordance withan embodiment of the present invention.

DETAILED DESCRIPTION

For purposes of promoting an understanding of the principles of theinvention, reference will now be made to the embodiments illustrated inthe drawings, and specific language will be used to describe the same.It will nonetheless be understood that no limitation of the scope of theinvention is intended by the illustration and description of certainembodiments of the invention. In addition, any alterations and/ormodifications of the illustrated and/or described embodiment(s) arecontemplated as being within the scope of the present invention.Further, any other applications of the principles of the invention, asillustrated and/or described herein, as would normally occur to oneskilled in the art to which the invention pertains, are contemplated asbeing within the scope of the present invention.

Referring to FIG. 1, there are illustrated some aspects of anon-limiting example of an aircraft 10 employed in accordance with anembodiment of the present invention. Aircraft 10 includes a fuselage 12,wings 14, an empennage 16, four gas turbine engine propulsion systems 18and two external pods 20. In one form, aircraft 10 is a multi-enginemilitary turboprop aircraft. In other embodiments, aircraft 10 may beany fixed-wing aircraft, including turbofan aircraft, turbojet aircraftand turboprop aircraft. In still other embodiments, aircraft 10 may be arotary-wing aircraft or a combination rotary-wing/fixed-wing aircraft.In various embodiments, aircraft 10 may have a single propulsion engineor a plurality of propulsion engines. In addition to propulsion engines,aircraft 10 may include one or more gas turbine auxiliary power units.In addition, in various embodiments, aircraft 10 may employ any numberof wings 14. Empennage 16 may employ a single or multiple flight controlsurfaces.

Referring to FIG. 2, aircraft 10 includes an airborne electrical powerand thermal management system 22, which is configured to provideelectrical power and manage thermal loads for a system 24. In one form,system 24 is a directed energy weapon system, such as a high power lasersystem, a high power microwave system and/or a high power millimeterwave system. In other embodiments, system 24 may include other aircraftelectrical and thermal loads. As illustrated in FIG. 2, in one form,system 22 is configured to provide electrical power to system 24, and toreceive thermal energy from system 24, e.g., heat energy rejected bysystem 24. In various embodiments, system 22 is partially or completelydisposed within an external pod 20, which, for example, may beretrofitted from use as an external fuel tank pod. In one form, externalpod 20 is configured to appear similar to a conventional external fueltank pod, e.g., in order to avoid altering of the appearance of aircraft10 or to minimize any alteration of the appearance of aircraft 10 due tothe inclusion of airborne electrical power and thermal management system22 and/or system 24.

Referring to FIG. 3, a non-limiting example of some aspects of anelectrical power and thermal management system 22 in accordance with anembodiment of the present invention is schematically depicted. In oneform, electrical power and thermal management system 22 includes acombustor 26, a turbine 28, a generator 30, a refrigerant compressor 32,a condenser 34, an expansion valve 36 and an evaporator 38 that isconfigured to chill a fluid, e.g., water. In some embodiments describedherein, combustor 26 and turbine 28 (via combustor 26) are supplied withpressurized air from one or more gas turbine engine propulsion systems18 in order to produce power to drive generator 30, refrigerantcompressor 32 and/or other components. In some embodiments, electricalpower and thermal management system 22 may include a complete gasturbine engine 39 disposed within pod 20, wherein engine 39 includes acompressor (not shown) in fluid communication with combustor 26, andturbine 28 in fluid communication with combustor 26. The compressor ofengine 39 may be supplied with ambient air, e.g., ram air, for example,via one or more openings (not shown) in pod 20, and/or may be suppliedwith pressurized air from a bleed air port of one or more gas turbineengine propulsion systems 18, e.g., a compressor bleed port. Refrigerantcompressor 32, condenser 34, expansion valve 36 and evaporator 38 areparts of a refrigeration system configured to handle the thermal loadsof system 24, e.g., by extracting heat from one or more components ofsystem 24.

In some embodiments, electrical power and thermal management system 22may include one or more other cooling systems to handle the thermalloads of system 24 in addition to or in place of a refrigeration system.For example, a cooling fluid may be circulated through or in proximityto one or more system 24 components to absorb heat from the system 24components. The cooling fluid may then be circulated through one or moreheat exchangers, e.g., air cooled heat exchangers disposed withinexternal pod 20, for removal of the heat from aircraft 10. Although manyor all components of the refrigeration system and/or other coolingsystem (e.g., one or more heat exchangers) may be disposed withinexternal pod 20, some such components may be located elsewhere inaircraft 10, i.e., not in external pod 20, including, for example andwithout limitation, one or more refrigerant and/or cooling fluid returnpumps. Although components of electrical power and thermal managementsystem 22 are depicted in certain locations and orientations withinexternal pod 20 in FIG. 3 (and in FIGS. 4 and 5), it will be understoodthat in various embodiments, components of electrical power and thermalmanagement system 22 and/or other components may be disposed in anydesired locations and orientations within external pod 20.

In one form, combustor 26, turbine 28, generator 30, refrigerantcompressor 32, condenser 34, expansion valve 36 and evaporator 38 arelocated within external pod 20. It will be understood that an electricalpower and thermal management system 22 and/or components thereof may bemounted in each external pod 20, and that the output of both may becombined in order to meet electrical power and thermal managementdemands of aircraft 10 and/or any weapon system installed therein and/ormounted thereon. In some embodiments, one or more of combustor 26,turbine 28, generator 30, refrigerant compressor 32, condenser 34,expansion valve 36 and evaporator 38 may be mounted in other locations.

Combustor 26 is in fluid communication with turbine 28. During theoperation of system 22, combustor 26 is supplied with pressurized airfrom a bleed port 40 of one or more gas turbine engine propulsionsystems 18, e.g., a compressor bleed port. Combustor 26 includes one ormore fuel injectors (not shown), which are supplied with fuel from afuel tank 42, e.g., an aircraft 10 fuel tank. Combustor 26 is configuredto mix the fuel with pressurized air received from bleed port 40 and toignite the mixture using one or more igniters (not shown). Combustor 26is configured to contain the combustion process, and to discharge thepressurized air, heated by the combustion process, into turbine 28.Turbine 28 is coupled to both generator 30 and refrigerant compressor32, and is operative to power both generator 30 and refrigerantcompressor 32 by extracting energy from the hot gases discharged fromcombustor 26. In one form, generator 30 and refrigerant compressor 32operate at the same rotational speed as turbine 28. In otherembodiments, one or more gearboxes may be interposed between turbine 28and generator 30 and/or refrigerant compressor 32 to drive generator 30and/or refrigerant compressor 32 at a different speed of rotation thanturbine 28.

Condenser 34 is fluidly coupled to the output of refrigerant compressor32. Condenser 34 is operative to condense the refrigerant discharged byrefrigerant compressor 32 during the operation of turbine 28. In oneform, ambient air, e.g., including ram air, is used as a coolant forextracting heat from condenser 34. In one form, an inlet scoop (notshown), e.g., a ram scoop (not shown) is employed to provide ambientair, e.g., ram air, for extracting heat from condenser 34. In otherembodiments, air and/or one or more other fluids may be employed toextract heat from condenser 34 via one or more other means. Expansionvalve 36 is fluidly coupled to the outlet of condenser 34, and isconfigured to expand the liquid refrigerant received from condenser 34,e.g., adiabatic expansion, which reduces the temperature of the liquidrefrigerant. In other embodiments, other means may be employed inaddition to or in place of expansion valve 36 to expand the liquidrefrigerant received from condenser 34.

Evaporator 38 is in fluid communication with condenser 34 via expansionvalve 36. In particular, the refrigerant inlet of evaporator 38 isfluidly coupled to expansion valve 36, and is operative to receive therefrigerant from expansion valve 36. The refrigerant outlet ofevaporator 38 is fluidly coupled to the inlet of refrigerant compressor32, and returns refrigerant vapor to the inlet of refrigerant compressor32. Evaporator 38 is configured to chill fluid for delivery to afuselage 12 mounted chilled fluid manifold 44. The chilled fluid outletof evaporator 38 is in fluid communication with chilled fluid manifold44. A recirculation pump (not shown) circulates a fluid, e.g., waterand/or one or more other suitable fluids through evaporator 38 andchilled fluid manifold 44, transmitting heat in the fluid from chilledfluid manifold 44 to evaporator 38. Chilled fluid manifold 44 is influid communication with a plurality of heat sources 46, 48 and 50, andis configured to distribute chilled fluid to heat sources 46, 48 and 50.Heat sources 46, 48 and 50 may be, for example and without limitation,system 24 components, such as a high power microwave module, a modulatorand an antenna module. In other embodiments, other components ofaircraft systems, weapon systems, propulsion systems and system 22 maybe cooled using the fluid chilled by evaporator 38, in addition to or inplace of those heat sources mentioned herein. The fluid outlets of heatsources 46, 48 and 50 are in fluid communication with evaporator 38.Chilled fluid from chilled fluid manifold 44 is employed to extract heatfrom heat sources 46, 48 and 50 to cool those components. The fluidheated by heat sources 46, 48 and 50 is then circulated through andre-chilled by evaporator 38.

Generator 30 is electrically coupled to one or more power conditioningunits 52, e.g., located in fuselage 12, for providing power in a desiredform for one or more electrically powered devices 54, only one of whichis illustrated for the sake of clarity. Conditioning unit 52 may be, forexample and without limitation, a DC/DC converter or any signalconditioning or power converting component. Device 54 may be, forexample and without limitation, a component of system 24, such as agyrotron or a cathode heater, high power microwave module, a modulatorand/or an antenna module or other directed energy weapon systemcomponent, or may be any electrical component. In some embodiments,electrical power and thermal management system 22 may include systemsfor storing energy and/or generating electrical power, in addition to orin place of generator 30, in order to supply power to one or moredevices 54. For example and without limitation, one or more batteries(not shown) and/or flywheel/motor/generator systems (not shown) and/orfuel cell systems may be employed to provide and/or store energy for useby one or more devices 54, e.g., to handle peak loads and/or to provideelectrical power to one or more devices 54 during startup of electricalpower and thermal management system 22. In various embodiments, suchsystems for storing energy may be disposed completely or partiallywithin external pod 20 or elsewhere within or on aircraft 10.

During operation, one or more devices 54 are powered by electrical powerand thermal management system 22, and one or more heat sources, such asheat sources 46, 48 and 50 are cooled by electrical power and thermalmanagement system 22.

Referring to FIG. 4, a non-limiting example of some aspects of anelectrical power and thermal management system 122 in accordance with anembodiment of the present invention is schematically depicted.Electrical power and thermal management system 122 employs many of thesame components for the same operations as set forth above with respectto electrical power and thermal management system 22, and hence, thedescription of such components, interconnections and operations is alsoapplicable to electrical power and thermal management system 122.

In addition to combustor 26, turbine 28, generator 30, refrigerantcompressor 32 and condenser 34, electrical power and thermal managementsystem 122 includes a refrigerant receiver 124, a refrigerantcirculation pump 126, an expansion valve 128, an evaporator 130 and athermal energy storage (TES) system 132. TES 132 may be any type ofsystem configured to store thermal energy, e.g., using one or moregases, liquids, solids and/or eutectic mixtures. Refrigerant receiver124 is in fluid communication with the outlet of condenser 34, and isoperative to receive liquid refrigerant from condenser 34. Recirculationpump 126 is in fluid communication with the outlet of refrigerantreceiver 124 and the inlet of expansion valve 128. The outlet ofexpansion valve 128 is in fluid communication with the fluid inlet ofevaporator 130. The vapor outlet of evaporator is in fluid communicationwith the inlet of refrigerant compressor 32.

Recirculation pump 126 is configured to pump liquid refrigerant toexpansion valve 128. Expansion valve 128 is configured to expand theliquid refrigerant. In other embodiments, other means may be employed inaddition to or in place of expansion valve 128 to expand the liquidrefrigerant received from condenser 34. Evaporator 130 is configured toremove heat from TES 132. TES 132 is configured to remove heat from aplurality of heat sources 134, 136 and 138, which may be, for exampleand without limitation, system 24 components, such as a high powermicrowave module, a modulator and an antenna module. In otherembodiments, other components of aircraft systems, weapon systems,propulsion systems and system 122 may be cooled by evaporator 130 andTES 132, in addition to or in place of those heat sources mentionedherein. It will be understood that an electrical power and thermalmanagement system 122 may be mounted in each external pod 20, and thatthe output of both may be combined in order to meet electrical power andthermal management demands of aircraft 10 and/or any weapon systeminstalled therein and/or mounted thereon, such as system 24.

Referring to FIG. 5, a non-limiting example of some aspects of anelectrical power and thermal management system 222 in accordance with anembodiment of the present invention is schematically depicted.Electrical power and thermal management system 222 employs many of thesame components for the same operations as set forth above with respectto electrical power and thermal management systems 22 and 122, andhence, the description of such components, interconnections andoperations is also applicable to electrical power and thermal managementsystem 222.

In addition to combustor 26, turbine 28, generator 30, refrigerantcompressor 32, condenser 34, refrigerant circulation pump 126, expansionvalve 128, evaporator 130 and TES 132, electrical power and thermalmanagement system 222 includes a refrigerant receiver 224, an expansionvalve 226, an evaporator 228, a heat exchanger 230, an expansion valve232, an evaporator 234, a controller/rectifier 236 for generator 30, anexpansion valve 238 and an evaporator 240. Refrigerant receiver 224 isconfigured to separate liquid refrigerant and refrigerant vapor, toreturn refrigerant vapor to the inlet of refrigerant compressor 32, andto supply liquid refrigerant to recirculation pump 126. Recirculationpump 126 is operative to circulate liquid refrigerant to the expansionvalve and evaporator associated with each item to be cooled. Forexample, expansion valve 226 is in fluid communication withrecirculation pump 126 and operative to receive liquid refrigerant fromrecirculation pump 126. Evaporator 228 is in fluid communication withexpansion valve 226 for receiving liquid refrigerant therefrom, and isin fluid communication with refrigerant receiver 224 for supplyingrefrigerant vapor thereto. Recirculation pump 126 supplies liquidrefrigerant to expansion valve 226, which is expanded and supplied toevaporator 228 for extracting heat from heat exchanger 230. In one form,heat exchanger 230 is a turbine 28 lube oil cooler, from which heat isextracted by evaporator 228. In other embodiments, heat exchanger 230may be employed for cooling one or more other mediums and/or componentsin addition to or in place of turbine 28 lube oil. The refrigerant vaporexiting evaporator 228 is returned to refrigerant receiver 224, fromwhere it is supplied to the inlet of refrigerant compressor 32.

Recirculation pump 126 also supplies liquid refrigerant to expansionvalve 232, which is expanded and supplied to evaporator 234 forextracting heat from controller/rectifier 236. In other embodiments,evaporator 234 may be employed for cooling one or more other componentsin addition to or in place of controller/rectifier 236. The refrigerantvapor exiting evaporator 234 is returned to refrigerant receiver 224,from where it is supplied to the inlet of refrigerant compressor 32.

Recirculation pump 126 also supplies liquid refrigerant to expansionvalve 238, which is expanded and supplied to evaporator 240 forextracting heat from generator 30. In other embodiments, evaporator 240may be employed for cooling one or more other components in addition toor in place of generator 30. The refrigerant vapor exiting evaporator240 is returned to refrigerant receiver 224, from where it is suppliedto the inlet of refrigerant compressor 32.

Recirculation pump 126 also supplies liquid refrigerant to expansionvalve 128, which is expanded and supplied to evaporator 130 forextracting heat from TES 132 for providing cooling of heat sources 134,136 and 138. In other embodiments, evaporator 130 may be employed forcooling one or more other components in addition to or in place of heatsources 134, 136 and 138. The refrigerant vapor exiting evaporator 130is returned to refrigerant receiver 224, from where it is supplied tothe inlet of refrigerant compressor 32.

Embodiments of the present invention include an airborne electricalpower and thermal management system, comprising: a turbine in fluidcommunication with a gas turbine engine bleed air source; a generatorpowered by the turbine and configured to provide power to an electricalload; a refrigerant compressor powered by the turbine; a condenser influid communication with the refrigerant compressor; and at least oneevaporator in fluid communication with the condenser, wherein the atleast one evaporator is configured to extract heat from at least oneheat source.

In a refinement, the electrical load includes a directed energy weaponsystem.

In another refinement, the at least one heat source includes a directedenergy weapon system.

In yet another refinement, the system further comprises a combustorfluidly disposed between the turbine and the bleed air source, whereinthe combustor is operative to mix fuel with air received from the bleedair source, combust the mixture, and discharge the combustion productsto the turbine.

In still another refinement, the at least one heat source is a pluralityof heat sources, further comprising a chilled fluid manifold, whereinthe at least one evaporator is configured to chill a fluid for deliveryto the chilled fluid manifold; and wherein the chilled fluid manifold isconfigured to distribute chilled fluid to the plurality of heat sources.

In yet still another refinement, the turbine, the generator, therefrigerant compressor and the condenser are disposed in an aircraftexternal pod.

In an additional refinement, the system further comprises a gas turbineengine disposed within the external pod, wherein the turbine is acomponent of the gas turbine engine.

In a further refinement, the system further comprises a refrigerantreceiver; a thermal energy storage system; and an evaporator in fluidcommunication with the refrigerant receiver and operative to receive aliquid refrigerant from the refrigerant receiver and extract heat fromthe thermal energy storage system.

In a yet further refinement, the system further comprises a refrigerantcirculation pump configured to pump the liquid refrigerant to thethermal energy storage system.

Embodiments of the present invention include an aircraft, comprising: afuselage; a wing coupled to the fuselage; an empennage coupled to atleast one of the fuselage and the wing; a gas turbine engine propulsionsystem coupled to the aircraft and having a bleed air port; an externalpod coupled to the aircraft; and an electrical power and thermalmanagement system at least partially disposed in the external pod,wherein the electrical power and thermal management system includes aturbine in fluid communication with the bleed air port; a generatorpowered by the turbine and configured to provide power to an aircraftelectrical load; a refrigerant compressor powered by the turbine; acondenser in fluid communication with the refrigerant compressor; and atleast one evaporator in fluid communication with the condenser, whereinthe at least one evaporator is configured to extract heat from at leastone heat source.

In a refinement, the at least one heat source includes components of adirected energy weapon system.

In another refinement, at least the turbine, the generator and therefrigerant compressor are disposed in the external pod.

In yet another refinement, the condenser is disposed in the externalpod.

In still another refinement, the condenser is configured for coolingwith ambient air supplied to the condenser from outside the externalpod.

In yet still another refinement, the condenser is configured for ram-aircooling.

In an additional refinement, the aircraft further comprises a combustorfluidly disposed between the turbine and the bleed air port, wherein thecombustor is operative to mix fuel with air received from the bleed airport, combust the mixture, and discharge the combustion products to theturbine.

In a further refinement, the at least one heat source is a plurality ofheat sources; wherein the at least one evaporator is a plurality ofevaporators corresponding in number to the plurality of heat sources;and wherein each evaporator of the plurality of evaporators isconfigured to extract heat from a corresponding each heat source of theplurality of heat sources.

In a yet further refinement, the aircraft further comprises arefrigerant circulation pump configured to pump liquid refrigerant tothe plurality of evaporators.

In a still further refinement, the aircraft further comprises arefrigerant receiver fluidly disposed between the condenser and therefrigerant circulation pump, wherein the refrigerant receiver isconfigured to accumulate liquid refrigerant.

In a yet still further refinement, the refrigerant receiver isconfigured to separate liquid refrigerant from refrigerant vapor.

In an additional refinement, the system further comprises a gas turbineengine disposed within the external pod, wherein the turbine is acomponent of the gas turbine engine.

Embodiments of the present invention include an aircraft, comprising: afuselage; a wing coupled to the fuselage; an empennage coupled to atleast one of the fuselage and the wing; a gas turbine engine propulsionsystem having a bleed air port; and means for providing electrical powerand thermal management, wherein the means for providing is in fluidcommunication with the bleed air port.

In a refinement, the aircraft further comprises an external pod, whereinthe means for providing is at least partially disposed in the externalpod.

In another refinement, the external pod is configured to appear similarto a conventional external fuel tank pod employed by the aircraft.

Embodiments of the present invention include an aircraft, comprising: afuselage; a wing coupled to the fuselage; an empennage coupled to atleast one of the fuselage and the wing; a gas turbine engine propulsionsystem coupled to the aircraft for providing propulsive thrust to theaircraft; an external pod coupled to the aircraft; and an electricalpower and thermal management system at least partially disposed in theexternal pod, wherein the electrical power and thermal management systemincludes a gas turbine engine disposed in the external pod; a generatorpowered by the gas turbine engine and configured to provide power to anaircraft electrical load; a refrigerant compressor powered by the gasturbine engine; a condenser in fluid communication with the refrigerantcompressor; and at least one evaporator in fluid communication with thecondenser, wherein the at least one evaporator is configured to extractheat from at least one heat source.

In a refinement, the external pod is configured to appear similar to aconventional external fuel tank pod employed by the aircraft.

While the invention has been described in connection with what ispresently considered to be the most practical and preferred embodiment,it is to be understood that the invention is not to be limited to thedisclosed embodiment(s), but on the contrary, is intended to covervarious modifications and equivalent arrangements included within thespirit and scope of the appended claims, which scope is to be accordedthe broadest interpretation so as to encompass all such modificationsand equivalent structures as permitted under the law. Furthermore itshould be understood that while the use of the word preferable,preferably, or preferred in the description above indicates that featureso described may be more desirable, it nonetheless may not be necessaryand any embodiment lacking the same may be contemplated as within thescope of the invention, that scope being defined by the claims thatfollow. In reading the claims it is intended that when words such as“a,” “an,” “at least one” and “at least a portion” are used, there is nointention to limit the claim to only one item unless specifically statedto the contrary in the claim. Further, when the language “at least aportion” and/or “a portion” is used the item may include a portionand/or the entire item unless specifically stated to the contrary.

What is claimed is:
 1. An airborne electrical power and thermalmanagement system, comprising: a first gas turbine engine having a firstcombustor, a first turbine and a bleed air port, the first gas turbineengine operable for producing propulsive power for an aircraft; a secondgas turbine engine including: a second combustor in fluid communicationwith the first gas turbine engine bleed air port; and a second turbinein fluid communication with the second combustor; a generator powered bythe second turbine and configured to provide electrical power to anelectrical load; a refrigerant compressor powered by the second turbine;a condenser in fluid communication with the refrigerant compressor; andat least one evaporator in fluid communication with the condenser,wherein the at least one evaporator is configured to extract heat fromat least one heat source; wherein the second gas turbine engine, thegenerator, the refrigerant compressor and the condenser are disposed inan aircraft external pod; wherein the at least one evaporator isdisposed in the aircraft external pod or an aircraft fuselage.
 2. Thesystem of claim 1, wherein the electrical load includes a directedenergy weapon system.
 3. The system of claim 1, wherein the at least oneheat source includes a directed energy weapon system.
 4. The system ofclaim 1, wherein the second combustor is operative to mix fuel with airreceived from the bleed air port, combust the mixture, and discharge thecombustion products to the second turbine.
 5. The system of claim 1,wherein the at least one heat source is a plurality of heat sources,further comprising a chilled fluid manifold, wherein the at least oneevaporator is configured to chill a fluid for delivery to the chilledfluid manifold; and wherein the chilled fluid manifold is configured todistribute chilled fluid to the plurality of heat sources.
 6. The systemof claim 1, further comprising a refrigerant receiver; a thermal energystorage system; and an evaporator in fluid communication with therefrigerant receiver and operative to receive a liquid refrigerant fromthe refrigerant receiver and extract heat from the thermal energystorage system.
 7. The system of claim 6, further comprising arefrigerant circulation pump configured to pump the liquid refrigerantto the thermal energy storage system.
 8. An aircraft, comprising: afuselage; a wing coupled to the fuselage; an empennage coupled to atleast one of the fuselage and the wing; a first gas turbine enginepropulsion system having a first combustor and a first turbine coupledto the aircraft and having a bleed air port; an external pod coupled tothe aircraft; and an electrical power and thermal management systemincluding a second gas turbine engine comprising a: second combustor influid communication with the bleed air port; and a second turbine influid communication with the second combustor; a generator powered bythe second turbine and configured to provide electrical power to anaircraft electrical load; a refrigerant compressor powered by the secondturbine; a condenser in fluid communication with the refrigerantcompressor; and at least one evaporator in fluid communication with thecondenser, wherein the at least one evaporator is configured to extractheat from at least one heat source wherein the second gas turbineengine, the generator, the refrigerant compressor and the condenser aredisposed in the external pod; wherein the at least one evaporator isdisposed in the external pod or the fuselage.
 9. The aircraft of claim8, wherein the at least one heat source includes components of adirected energy weapon system.
 10. The aircraft of claim 8, wherein thecondenser is configured for cooling with ambient air supplied to thecondenser from outside the external pod.
 11. The aircraft of claim 10,wherein the condenser is configured for ram-air cooling.
 12. Theaircraft of claim 8, wherein the second combustor is operative to mixfuel with air received from the bleed air port, combust the mixture, anddischarge the combustion products to the second turbine.
 13. Theaircraft of claim 8, wherein the at least one heat source is a pluralityof heat sources; wherein the at least one evaporator is a plurality ofevaporators corresponding in number to the plurality of heat sources;and wherein each evaporator of the plurality of evaporators isconfigured to extract heat from a corresponding each heat source of theplurality of heat sources.
 14. The aircraft of claim 13, furthercomprising a refrigerant circulation pump configured to pump liquidrefrigerant to the plurality of evaporators.
 15. The aircraft of claim14, further comprising a refrigerant receiver fluidly disposed betweenthe condenser and the refrigerant circulation pump, wherein therefrigerant receiver is configured to accumulate liquid refrigerant. 16.The aircraft of claim 15, wherein the refrigerant receiver is configuredto separate liquid refrigerant from refrigerant vapor.
 17. An aircraft,comprising: a fuselage; a wing coupled to the fuselage; an empennagecoupled to at least one of the fuselage and the wing; a fuel tank; afirst gas turbine engine propulsion system having a bleed air port and afirst combustor to provide energy for aircraft propulsion; an electricalpower and thermal management system including a second gas turbineengine, at least one evaporator, a refrigerant compressor, and acondenser, wherein the second gas turbine engine has a second combustorto provide energy for electrical power and thermal management, andwherein the second combustor is in fluid communication with the bleedair port of the first gas turbine engine and the fuel tank; and anexternal pod, wherein the second gas turbine engine, the refrigerantcompressor, and the condenser of the electrical power and thermalmanagement system are disposed in the external pod; wherein the at leastone evaporator is disposed in the external pod or the fuselage.
 18. Theaircraft of claim 17, wherein the external pod is configured to appearsimilar to a conventional external fuel tank pod employed by theaircraft.
 19. An aircraft, comprising: a fuselage; a wing coupled to thefuselage; an empennage coupled to at least one of the fuselage and thewing; a first gas turbine engine propulsion system having a firstcombustor and a first turbine coupled to the aircraft for providingpropulsive thrust to the aircraft; an external pod coupled to theaircraft; and an electrical power and thermal management systemincluding a second gas turbine engine having a second combustor and asecond turbine; a generator powered by the second gas turbine engine andconfigured to provide electrical power to an aircraft electrical load; arefrigerant compressor powered by the second gas turbine engine; acondenser in fluid communication with the refrigerant compressor; and atleast one evaporator in fluid communication with the condenser, whereinthe at least one evaporator is configured to extract heat from at leastone heat source wherein the second gas turbine engine, the generator,the refrigerant compressor and the condenser are disposed in theexternal pod; wherein the at least one evaporator is disposed in eitherthe external pod or the fuselage wherein the aircraft electrical loadand the at least one heat source are disposed in the fuselage.
 20. Theaircraft of claim 19, wherein the external pod is configured to appearsimilar to a conventional external fuel tank pod employed by theaircraft.